Aeroplane brake



Feb. 9 1926, 1,572,361

R. J. PICK, JR

- AEROPLANE BRAKE Filed May 26. 1925 wventox J. may

Patented eb. 9, 1926.

UNITED STATES PATENT OFFICE.

RUDOLPH J. PICK, JR., OF CHICAGO, ILLINOIS.

' AEBOPLANE BRA XE.

Application filcd May 26, 1925. Serial No. 32,998.

ful Improvements in an,Aeroplane Brake,

- ofwhich the following is a specification.

END

This invention relates to improvements in aeroplanes, and is mof particularly adapted to a brake mechanism therefor tofacilitate the stopping of an aeroplane after the same has descended and has alighted on the landing surface. p

A further object of the inventionis to provide an aeroplane brake of the above mentioned character which includes a pair of drag fins or planes which are pivotally supported at their rear ends on the opposite sides of the fuselage of the aeroplane, means being provided for normally holding the fins or planes in an inoperative position, said fins being adapted to be automatically swung laterally with respect to the fuselage whereby the forward movement of the aeroplane after the same has landed will be retarded. J y

A still further object is to provide an aeroplane brake of the above mentioned character which includes a means for releasing the latch mechanism associated with the fins,said release means being disposed within easy access of the ilot'of the aeroplane.

A still further Ob]80t is to provide an aeroplane brake of the above mentioned character which will at all times be positive and efficient in its operation, the same being further simple in construction, inexpensive, strong and durable, and further well adapted to the urposes for which it is designed.

Other 0 jects and advantages of this invention will become apparent during the course of the following description.

In the accompanying drawing forming a part of this application and in which like numerals designate like parts throughout the same':

Figure 1 is a fragmentary side elevation of the fuselage of an aeroplane showing my improved brake mechanism associated therewith, and the same being in its normally inoperative position, and

Figure 2 is a top plan view showing the brake "mechanism 111 an operativeposition.

In the drawing, wherein for the purpose of illustration is shown the referred embodiment of my invention, t e numeral 1 designates a portion of the fuselage offan aeroplane, the cock pit being illustrated generally at 2. The sides of the fuselage are provided with substantially rectangular cut out portions, the same being preferably formed in the. tailportion of the fuselage. Arranged in the cutout portion are the drag fins or planes 3 and 4 respectively.

Both of the drag fins or planes are hinged at their rear ends to the body or fuselage of the aeroplane as illustrated at 5. A latch receiving keeper 6 is provided on the inner side of each of the drag fins or plane adja cent the forward free end of each of the fins 0r planes, and the purpose thereof will hereinafter be more fully described. latch mechanism which is provided for normallyholding the dragjfins or planes in a closed or inoperative position comprises a curved spring wire 7 which encircles the forward portion of the cock pit 2. The free ends 8 of the curved spring wire 7 are dis posed through suitable guides 9 which are arranged at opposite sides of the cock pit and the free ends 8 are adapted to be received in the respective keepers 6 as is illustrated more clearly in Figure 1.

For the purposes of limiting the outward swinging movement of the drag fins or planes, I providea stationary eye member 10, which is supported in the fuselage 1 forwardlyof the rear ends ofthe fins or planes. The. free end of the drag fin or plane 3 is connected to the stationary eye bolt 10 through the medium of the cables 11 and 12, and a similar pair of cables 13 and 14 respectively affords a connection between the outer end of the opposite drag fin or plane with the stationary eye member 10. Normally, the drag fins or planes are maintained in a closed or inoperative position,

so that the outer faces of the fins or planes will lie flush with the outer faces of the sides of the fuselage, and the latch mechanism "will maintain the drag fins in an inoperative or closed position, so that the aeroplane may be used' in the usualmanner, and the drag fins or planes will'not in anyway retard the forward movement of the" aeroplane while in flight. 7

As an aeroplane having my, improved brake mechanism associated therewith descends, and alights on the landing surface,

8 thereo to become disengaged from the The keepers 6, and the drag fins or planes will thenautomatically swing laterally to an operative position as is shown in Figure 2 of the drawing so as to be disposed at substantially right angles to the fuselage, the cables limiting the outward swinging movement of the drag fins or planes so as to prevent the drag fins from swinging rearwardly against the sides of the tail of the fuselage. When the drag fins or planes are in the position as shown in Figure 2 of the drawings,

the same will act as an arrestor and retard 1 the forward movement of the aeroplane departing from the spirit of the invention and the scope of the appended claims.

Having thus described the invention what I claim as new and desire to secure by Letters Patent is:

1. A brake mechanism for aeropianes comprising a pair of drag fins hingedlysupported at their rear ends on opposite sides of the fuselage of an aeroplane, the fuselage being provided with cut out portions in the sides for the reception of the drag fins when the latter are in a closed position. means for holding the drag fins in a closed inopeiative position, said means comprising a pair of keepers arranged on the inner 'SldGS of the respective drag fins adjacent the forward free ends thereof, a curved spring wire latch member, the free ends thereof adapted to extend into the keepers, said latch member adapted to be moved forwardly whereby the free ends thereof are disenga ed from the keeper to permit the outwar swinging movement of the drag fins to an operative position, and means for limiting the outward swinging movement of the drag fins. I

2. A brake mechanism for aeroplanes comprising a pair of drag fins hingedly supported at their vrear ends on opposite sides of the fuselage of an aeroplane, the fuselage being provided with cut out portions in the sides for the reception of the drag fins when the latter are in a closed position, means for holding the drag fins in a closed inoperative position, said means comprising a pair of keepers arranged on the inner sides of the respective drag fins adjacent the forward free ends thereof, a curved spring wire latch member, the free ends thereof adapted to extend into the keepers, said latch member adapted to be'moved forwardly where y the free ends thereof are disengaged from the keeper to permit the outward swinging movement of the drag fins to an operative position, means for limiting the outward swinging movement of the drag fins, said last-mentioned means comprising a pair of cables secured at their outer ends to the'out- ,er portions of the respective drag fins, the

inner ends of the cables being secured to. the fuselage.

In testimony whereof I afiix my signature.

RUDOLPH J. PICK, JR. 

